Arrow for aerodynamically stabilizing a payload in flight

ABSTRACT

A system and method for propelling pellets from a launch tube in flight includes a payload section and a stabilizing section. The launch tube and its pellets are essentially the payload section. The stabilizing section is essentially the equivalent of an arrow, and it includes a connector for selectively engaging the stabilizing section with the payload section. In use, the stabilizing section is reusable with a sequence of payload sections.

This application is a continuation-in-part of application Ser. No.13/298,124 filed Nov. 16, 2011, which is currently pending. The contentsof application Ser. No. 13/298,124 are incorporated herein by reference.

FIELD OF THE INVENTION

The present invention pertains generally to man-powered weapons. Moreparticularly, the present invention pertains to systems and methods forshooting a plurality of pellets (i.e. projectiles or shot) at a targetwith a statistically predictable and defined shot group on the target.Further, the present invention pertains to devices for stabilizingpellet-cluster payloads, in flight, prior to a separation of the pelletsfrom the stabilizing device. The present invention is particularly, butnot exclusively, useful as a system and method for propelling amulti-pellet-filled launch tube from a man-powered weapon, and foremploying the resultant acceleration force on the launch tube to unlatchand release the pellets from the launch tube for impact in a shot groupon a target.

BACKGROUND OF THE INVENTION

Typically, man-powered weapons are designed to launch only oneprojectile at a time. In particular, this is the case when the weapon isto be operated and fired by a single individual. For example, the arrowof a well-known bow and arrow set is such a projectile, as is the boltof a crossbow or the dart of a blowgun. There are instances, however(e.g. the extermination of vermin or clay pigeon shooting), when itwould be preferable to simultaneously launch several projectiles (e.g.pellets) all at the same time. In this respect, there is a need for aman-powered weapon that is comparable in its on-target effect to thefamiliar shotgun. To achieve such comparability with a man-poweredweapon, like a shotgun, all of the pellets need to be collectivelylaunched as a predictably defined group. The situation for a man-poweredweapon is exacerbated, however, due to the fact that they typicallyemploy only a single launching string or, in the case of an air gun, asingle launching tube.

Ideally, when a plurality of projectiles are to be launchedsimultaneously from a single man-powered weapon, the launching mechanismof the weapon needs to have comparably direct influence upon eachprojectile (e.g. pellet). Specifically, the influence and control overeach projectile in the plurality must be similar, and be effective tothe same extent, as if only one projectile was being launched. Ithappens, however, that with a single string or single barrel launcher(e.g. a bow, a crossbow or an air gun), such influence and control isvirtually impossible. A solution for this problem is to, somehow,structurally combine the several projectiles into a cohesive unit forlaunch. This solution, of course, must be short term. Immediately afterlaunch, the problem then becomes how to effectively separate theprojectiles. Specifically, this separation must be accomplished in amanner that causes the projectiles to travel toward a target in apredictably defined group that will have the intended on-target effect.

As a cost saving feature, it is desirable there be a system componentthat can be used, and reused. For the present invention, this componentis envisioned to be a stabilizing section (i.e. an arrow) that providesinitial aerodynamic stability for a payload of multiple pellets(projectiles). Specifically, the stability provided by this stabilizingsection (arrow) is required immediately after a launch, but before thereis pellet separation from the payload. Furthermore, depending on thetarget, on the capabilities of the user, and on the situationalcircumstance, it may be desirable that the user be able to select aparticular payload. More specifically, it may be desirable to select apayload having a predetermined number of pellets in the payload, whereinthe pellets are of a specific size.

With the above in mind, it is an object of the present invention toprovide a multi-pellet launcher that will hold a plurality ofprojectiles together as a single cohesive unit prior to and duringlaunch. Another object of the present invention is to provide amulti-pellet launcher that will maintain a group integrity for thepellets (projectiles) while in flight, for the purposes of achieving anintended on-target effect (i.e. have a statistically well defined shotgroup). Yet another object of the present invention is to provide areusable, aerodynamic stabilizing section that is individuallyengageable with different selected multi-pellet launchers (i.e.payloads). Still another object of the present invention is to provide amulti-pellet launcher that is easy to use, is simple to manufacture, andis cost effective.

SUMMARY OF THE INVENTION

In accordance with the present invention, a system is provided forpropelling pellets (projectiles) from a launch tube. In particular, thepropulsion of pellets occurs after the launch tube has been shot from aman-powered weapon (e.g. a bow, a crossbow or an air gun). Prior tobeing shot (launched), the launch tube holds a plurality of pelletsinside the tube. Specifically, this is accomplished by positioning thepellets between a retainer plug that is restrained inside the launchtube, and a compression spring that is fixedly mounted inside the launchtube. In order to restrain the retainer plug, a latch is establishedrelative to the launch tube. The latch then prevents a forward movementof the retainer plug, and the pellets, in response to a bias force thatis imposed on the retainer plug and the pellets by the partiallycompressed spring.

In overview, while the launch tube is being propelled in a forwarddirection by a man-powered weapon, the resultant acceleration force onthe launch tube moves the retainer plug and pellets in a relativelyrearward (proximal) direction with respect to the tube. This proximalmovement of the retainer plug and pellets in the launch tube furthercompresses the spring, and simultaneously releases the latch from theretainer plug. In flight, after the initial acceleration force hassubsided, the compressed spring provides a forward propulsion force onthe plurality of pellets and the retainer plug. This propulsion forcethen ejects the pellets and the retainer plug from the launch tube. Thepellets then continue on toward an intended target.

Structurally, the launch tube of the present invention is formed with alumen, and it defines a longitudinal axis. In a preferred embodiment ofthe present invention, it also has an open distal end and a closed orpartially closed proximal end. Beginning at the proximal end of thelumen inside the launch tube, the spring is positioned and affixed toits closed proximal end. The plurality of pellets (projectiles) is thenpositioned in the lumen against the spring. Next, the retainer plug ispositioned in the lumen distal to the plurality of pellets(projectiles). In greater structural detail, for one embodiment of thepresent invention, the retainer plug has a distal ring that isdimensioned to move within the lumen, and it has a proximal ring that isalso dimensioned to move within the lumen. Between these rings of theretainer ring is a mid-section that is formed with a decreasing taper inthe proximal direction.

In the vicinity of the retainer plug, the sidewall of the launch tube isformed with one or more lateral vents. Preferably, these vents arelocated equidistant from the distal end of the tube. One or more latchspheres are provided to interact between the proximal ring of theretainer plug and the vents of the launch tube. Specifically, thisinteraction is in response to the distally directed force that isgenerated when the spring is partially compressed. More specifically,each latch sphere is trapped in a respective vent, and it is urgedagainst a distal edge of the vent by the proximal ring of the retainerplug. Thus, prior to a launch, the distal bias of the compressed springon the retainer plug holds the retainer plug, and the pellets,stationary in the lumen of the launch tube.

Upon shooting a launch tube from a man-powered weapon, an accelerationforce is imposed in a distal direction on the pellets, and on theproximal end of the spring within the lumen of the launch tube. Thisacceleration causes the retainer plug and pellets to move proximallyrelative to the launch tube, and the spring is further compressed. Inturn, this relative motion of the retainer plug and launch tube causesthe proximal ring of the retainer plug to release the latch sphere(s)and causes a tapered or stepped region of the retainer plug to eject thelatch sphere(s) from the launch tube through their respective vents.Consequently, the retainer plug and the plurality of pellets arereleased by the latch and are propelled from the launch tube in responseto the distal bias of the spring.

An additional structure of the launch tube is an inner sleeve that canbe affixed inside the lumen of the launch tube, proximal to the spring.Specifically, this inner sleeve is positioned at a distance “d_(f)” fromthe distal end of the launch tube to act as an abutment for the springwhen it is compressed. The distance “d_(f)” can, of course, be varied asdesired. In any event, it is preferable that the inner sleeve be affixedto place the pellets (projectiles) relatively near the distal end of thelaunch tube. With this in mind, the present invention envisions that,even though the pellets may extend through a relatively short distance(i.e. a few inches), an inner sleeve will allow the total length of thelaunch tube to be as long as is required for a conventional bow,compound bow or crossbow.

For a preferred embodiment of the present invention, there may be asmany as forty or more pellets, and they can be made of steel. Also, inorder to promote tumbling of the retainer plug after a launch of thelauncher, the distal ring of the retainer plug may be formed with adistal recessed surface, and is made of a light-weight material such asAcrilonitrile-Butadiene-Styrene (ABS), Polycarbonate or Polysulfone.Also, for the purpose of dispensing the pellets in-flight for acontrolled, on-target impact, the pellets inside the launch tube can becombined with a plurality of spacers. If used, individual spacers can bepositioned between adjacent pellets in the launch tube. In anotherembodiment, for the same purpose, a plurality of magnets can be combinedwith the pellets in a configuration where adjacent magnets straddle twopellets, and pellets on opposed sides of a same magnet are subjected toa different polarity.

For an alternate embodiment of a latch for the multi-pellet launcher,the launch tube is formed with a pair of axially opposed slots thatextend, parallel to each other, in a proximal direction from the distalend of the launch tube. A detent is formed at the proximal end of eachslot. For this embodiment, the retainer plug is cylindrical and includesa pair of axially opposed pins that extend outwardly from the retainerplug. For an assembly of the multi-pellet launcher in accordance withthis alternate embodiment, the pins on the retainer plug are received ina respective slot of the launch tube and are advanced in a proximaldirection. When the pins are at the proximal end of their respectiveslots, the retainer plug is rotated to engage the pins with a respectivedetent at the end of the slot. This holds the retainer plug stationaryin the launch tube. Upon a subsequent launching of the launch tube, theresultant acceleration force rotates the pins out of their detents. Thisthen frees the retainer plug for axial movement out of the launch tubein a distal direction when the acceleration force subsides. It is animportant consideration for this particular embodiment of the latch,that the pins do not extend beyond the outer diameter of the launch tubewhen the retainer plug is engaged with the launch tube. This isnecessary to allow an assembled launcher to be received within thebarrel of a weapon (e.g. an air gun) without any interference of thepins on the retainer plug with the bore of the barrel.

In yet another embodiment of a latch for the present invention, thelaunch tube is formed with at least one lateral opening. For thisembodiment, the retainer plug includes a clip that is mounted on theretainer plug, and the clip is reconfigured to engage with the lateralopening. Importantly, the clip does not extend beyond the lateralopening. When the launch tube is launched, as in the other embodimentsof the present invention, the resultant acceleration force moves theretainer plug in a proximal direction relative to the launch tube.Consequently, the clip is released from the lateral opening. Theretainer plug is thereby released for free travel through the launchtube.

In yet another alternate embodiment that is within the scope of thepresent invention, a system is provided for launching a pellet-clusteronto a flight path from a man-powered weapon that includes reusablecomponents. Such a system includes a payload section as substantiallydisclosed above, and a reusable stabilizer section (i.e. an arrow). Asbefore, the payload section carries pellets in a pellet-cluster for anin-flight release of the pellet-cluster from the payload section. Forthis particular embodiment of the present invention, however, thepayload section is selectively engageable with the stabilizer section.Structurally, the stabilizer section includes a shaft that defines alongitudinal axis and has an aft-end and a fore-end. A plurality offletches are attached to the aft-end of the shaft to establish anempennage for stabilizing the shaft and payload section during flight.Further, a connector is affixed to the fore-end of the shaft. Asenvisioned for the present invention, the payload section is formed withan insert extension and the connector is formed as an insert receptaclefor receiving the insert extension therein to hold the payload on thearrow. With this structure, the engagement of the payload with the arrowmay be either a friction fit or a bayonet fit. When assembled, thepayload section and the stabilizer section will typically have anoverall length that is between four and thirty two inches.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features of this invention, as well as the invention itself,both as to its structure and its operation, will be best understood fromthe accompanying drawings, taken in conjunction with the accompanyingdescription, in which similar reference characters refer to similarparts, and in which:

FIG. 1 is a side elevation view of a multi-pellet launcher in accordancewith the present invention;

FIG. 2A is a perspective view of a launcher of the present inventionduring mid-launch from a crossbow;

FIG. 2B is a plan/elevation view of the launcher of the presentinvention prepared for launch from a bow;

FIG. 3 is a plan/elevation view of an air gun for use with the presentinvention;

FIG. 4A is a cross-section view of the multi-pellet launcher as seenalong the line 4-4 in FIG. 1 prior to launch;

FIG. 4B is a cross-section view of the multi-pellet launcher as seen inFIG. 4A as the launcher is being accelerated during launch;

FIG. 4C is a cross-section view of the multi-pellet launcher as seen inFIG. 4B after launch;

FIG. 5 is a cross-section view of an alternate embodiment of amulti-pellet launcher as would be seen along the line 4-4 in FIG. 1;

FIG. 6 is a cross-section view of another embodiment of the multi-pelletlauncher as seen along the line 4-4 in FIG. 1;

FIG. 7A is an exploded perspective view of an alternate embodiment of alaunch tube and retainer plug for use with the present invention, withthe retainer plug positioned for engagement with the launch tube;

FIG. 7B is a view as shown in FIG. 7A with the retainer plug engagedwith the launch tube;

FIG. 8A is a cross-section view of a launcher as seen along the line 8-8in FIG. 7A prior to a launch;

FIG. 8B is a cross-section view of the launcher shown in FIG. 8A,immediately after a launch;

FIG. 8C is a front-on view looking into the launch tube of the launcher;

FIG. 8D is a cross-section view of an alternate embodiment for the innersleeve shown in FIG. 8A, prior to launch;

FIG. 8E is a cross-section view of the inner sleeve shown in FIG. 8D,immediately after launch;

FIG. 9A is a cross-section view of another alternate embodiment of alaunch tube and retainer plug prior to a launch;

FIG. 9B is a cross-section view of the launch tube shown in FIG. 9Aimmediately after a launch;

FIG. 10 is a perspective view of a spring guide for use with the springin an alternate embodiment of the present invention;

FIG. 11A is a cross sectional view of a launcher using a spring guide,as seen along the line 8-8 in FIG. 7A, prior to launch;

FIG. 11B is a view of the launcher shown in FIG. 11A immediately afterlaunch;

FIG. 12A is an exploded perspective view of a reusable, aerodynamicstability section, positioned for engagement with a launcher of thepresent invention; and

FIG. 12B is an exploded perspective view of an alternate embodiment of areusable, aerodynamic stability section, positioned for engagement witha launcher of the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring initially to FIG. 1, a multi-pellet launcher in accordancewith the present invention is shown and is generally designated 10. Asshown, the launcher 10 includes a hollow, elongated launch tube 12 thathas a distal end 14 and a proximal end 16. For the launcher 10, thedistal end 14 of launch tube 12 is open, and its proximal end 16 isclosed or partially closed. For purposes of disclosure, the launch tube12 defines a longitudinal axis 18 that extends between the distal end 14and the proximal end 16. As intended for the present invention, thelauncher 10 can be used as a bolt for a crossbow 20 (see FIG. 2A), as anarrow for a bow 22 (see FIG. 2B) or as a launch tube 12 to be used withan air gun 23 and launched from its barrel 25 (see FIG. 3). In allimportant respects, the multi-pellet launcher 10 will be essentially thesame regardless of the type of man-powered weapon that is to be used(i.e. crossbow 20, bow 22 or air gun 23).

Referring now to FIG. 4A, a launcher 10 is shown in greater detail toinclude a nock 24 at its proximal end 16 and a flight stabilizer 26 thatwill stabilize the launch tube 12 during its flight. Other structuralaspects of the launcher 10 are discussed with reference to the lumen 28of the launch tube 12, and begin with an inner sleeve 30 that is fixedlyattached to the launch tube 12, inside the lumen 28. Referring for themoment back to FIG. 1, it will be seen that the inner sleeve 30 ispositioned in the lumen 28 of the launch tube 12 at a distance “d_(f)”from the distal end 14 of the launch tube 12. FIG. 1 also indicates thatthe inner sleeve 30 is positioned at a distance “d_(a)” from theproximal end 16 of the launch tube 12.

FIG. 4A also shows that a spring 32 is positioned in the lumen 28immediately distal the inner sleeve 30, and between the inner sleeve 30and a plurality of pellets 34. As intended for the launcher 10, theremay be six or more pellets 34. The pellets 34 shown in the drawings areonly exemplary. It will be appreciated that the distance “d_(f)” willdepend primarily on the number of pellets 34 that are to be used. On theother hand, the distance “d_(a)” may vary considerably, depending on thetype of man-powered weapon to be used. As envisioned for the presentinvention, the overall length of the launcher 10 (i.e. d_(f)+d_(a)) maybe as long as twenty nine or thirty inches.

Positioned distal to the pellets 34 is a retainer plug 36 that ispreferably made of a light weight material such asAcrilonitrile-Butadiene-Styrene (ABS), Polycarbonate or Polysulfone.Structurally, the retainer plug 36 is formed with a proximal ring 38 anda distal ring 40, with a mid-section 42 formed therebetween.Importantly, both the proximal ring 38 and the distal ring 40 aredimensioned for movement within the lumen 28 of the launch tube 12.Further, it is important that the mid-section 42 be formed with adecreasing taper in the proximal direction from the distal ring 40 tothe proximal ring 38.

As perhaps best seen in FIG. 4B, the launch tube 12 is formed with oneor more vents 44. In FIG. 4B, the vents 44 a and 44 b are onlyexemplary, as there may be more vents 44 if desired. Both FIGS. 4A and4B, however, show that each vent 44 interacts with a respective latchsphere 46. Again, like the vents 44 a and 44 b, the latch spheres 46 aand 46 b are only exemplary. Despite the number of vents 44 and latchspheres 46 that may be used, it is to be appreciated that each latchsphere 46 interacts individually with the retainer plug 36 and with itsrespective vent 44. Importantly, the purpose of these interactions is tohold the pellets 34 in the lumen 28 of the launch tube 12 prior to alaunch. Specifically, FIG. 4A shows that prior to a launch, each of thelatch spheres 46 is trapped (wedged) between the proximal ring 38 of theretainer plug 36 and the forward (distal) edge of a vent 44. Thisstructural interaction changes dramatically with a launch of the launchtube 12.

As a launch tube 12 is launched from a crossbow 20, or bow 22, in thedirection of arrow 47 (see FIG. 4B) an acceleration force is generatedthat will cause the retainer plug 36 and the plurality of pellets 34 tomove in a proximal direction inside the lumen 28 of the launch tube 12.With this movement, several things happen. For one, the spring 32 isfurther compressed. For another, as the retainer plug 36 moves in theproximal direction, the proximal ring 38 of retainer plug 36 disengagesfrom the latch spheres 46. As this happens, the tapered mid-section 42of the retainer plug 36 ejects the latch spheres 46 away from the launchtube 12, through their respective vents 44. A consequence of this isthat both the retainer plug 36 and the pellets 34 are no longer confinedin the lumen 28 of the launch tube 12.

Shortly after launch, in accordance with well known principles, theinitial acceleration force on the launch tube 12 subsides. With thisdiminution of the acceleration force, the potential energy in thecompressed spring 32 is released to propel the retainer plug 36 andpellets 34 from the launch tube 12. As shown in FIG. 4C, after beingpropelled from the launch tube 12 by the spring 32, the retainer plug 36separates and tumbles away from the pellets 34. To assist in thisseparation and tumbling behavior, the distal face 48 of retainer plug 36can be formed with a recessed (concave) surface. In any event, thedesired result is that the plurality of pellets 34 will then follow aplanned trajectory toward a target (not shown), for an intendedon-target affect. An important consideration here is that the pellets 34need to also achieve a degree of separation from each other for thecreation of the desired on-target shot group.

For an alternate embodiment of the launcher 10, as shown in FIG. 5, aplurality of spacers 50 can be employed to help with the separation ofpellets 34 after launch. The spacers 50 a and 50 b shown in FIG. 5 areexemplary. If used, the spacers 50 will typically be positioned tostraddle each pellet 34 in a manner such as is shown for the spacers 50a and 50 b. Preferably, the spacers 50 will be made of a light weightmaterial such as felt or paper. In another alternate embodiment of thelauncher 10 for this same purpose, as shown in FIG. 6, a plurality ofmagnets 52 can be employed. In this embodiment, a pair of magnets (e.g.magnets 52 a and 52 b) will straddle a pair of pellets (e.g. pellets 34a and 34 b). For best effect, within this structure, the opposed sidesof the magnets 52 a and 52 b will have the same polarity. Thus, themagnets 52 (magnets 52 a and 52 b are exemplary) will add a repellingforce on the pellets 34 a and 34 b that will influence their separationin flight.

An alternate embodiment for the structure of a latch to be used with thepresent invention is shown in FIGS. 7A & 7B. In FIG. 7A it will be seenthat a launch tube 54 has a proximal end 56 and a distal end 58, with apair of opposed parallel slots 60 a and 60 b that extends in a proximaldirection from the distal end 58. Further, with reference to the slot 60a in FIG. 7A, it is seen that the end of the slot 60 a is formed with adetent 62, and an angled edge 64 extends in a proximal directiontherefrom. FIG. 7A also shows a cylindrical shaped retainer plug 66 thatincludes a pin 68 which extends outwardly from the plug 66. Actually,there is a pair of opposed pins 68 (one is not shown). With reference toFIG. 7B, it will be appreciated that during an assembly of the retainerplug 66 with the launch tube 54, the pin(s) 68 is(are) inserted into therespective slots 60 a and 60 b. They are advanced through the slots 60 aand 60 b, and the retainer plug 66 is then rotated to seat the pin(s) 68against the detent(s) 62.

In an operation of the launch tube 54, the acceleration force thatinitially results during a launch of the launch tube 54 will cause theretainer plug 66 to move in a rearward (proximal) direction relative tothe launch tube 54. This relative movement of the retainer plug 66 thencauses the pin 68 to follow the angled edge 64. The result here is thatthe retainer plug 66 is rotated to realign the pin 68 with the slot 60a, and to thereby allow for a free distal (forward) movement of theretainer plug 66 out of the launch tube 54 when the acceleration forcesubsides. An important aspect of this particular embodiment of alatching action for the present invention is that the pin(s) 68 do notextend beyond the outer surface 70 of the launch tube 54. This is so inorder to allow for an assembled launch tube 54 to be positioned in ahollow launch tube (not shown), such as in the barrel of an air gun 23.Additionally, it will be appreciated by the skilled artisan that theinside surface 72 of the barrel 25 of air gun 23 can be rifled to assistin the proper rotation and alignment of the retainer plug 66 during anoperation of this embodiment of the present invention.

FIG. 8A shows an alternate configuration for components inside thelaunch tube 12/54. One component of interest is the inner sleeve 74. Asshown, the inner sleeve 74 is positioned inside the launch tube 12/54,and is preferably located at or near the proximal end 56. Further, theinner sleeve 74 includes an abutment 76 that establishes a hollow 78 forthe inner sleeve 74. Within this structure, the spring 32 is positionedbetween the abutment 76 and a washer 80. Importantly, when sopositioned, a portion of the spring 32 will be inside the hollow 78.Thus, as shown in FIG. 8B, when the spring 32 is compressed by a forceof acceleration (represented by arrow 82 in FIG. 8B), compression of thespring 32 is controlled. Specifically, during a launch of the launchtube 12/54, the compression of spring 32 will be limited by theconstraints imposed on it by dimensions of the hollow 78 inside theinner sleeve 74. FIGS. 8A and 8B also indicate that the abutment 76 ofthe inner sleeve 74 can be formed with an opening 84. Opening 84,however, is optional. Indeed, when the launch tube 54 is to be used withan air gun (not shown), it is preferable that the opening 84 be closed.

Still referring to FIGS. 8A and 8B, an arrangement for stacking pellets34 (e.g. pellets 34 c-f) within a launch tube 12/54 is shown. In detail,by cross referencing FIG. 8B with FIG. 8C, a stacking arrangement for arelatively large number of the pellets 34 (e.g. thirty or more pellets34) is shown. In particular, this stacking arrangement is possible wheneach of the pellets 34 has a diameter “d_(p)” that is slightly less thanhalf the inner diameter “d_(i)” of the launch tube 12/54 (see FIG. 8C).For purposes of disclosure, specific reference is made to pellets 34 c,34 d, 34 e and 34 f (only pellets 34 c, 34 d and 34 f are shown in FIG.8B). With FIGS. 8B and 8C, it will be appreciated that the pellets 34 cand 34 e are essentially positioned inside the launch tube 12/54,side-by-side. Likewise, the pellets 34 d and 34 f are also side-by-side.In order to easily achieve this stacking configuration during loading,the pellets 34 c-f can be introduced into the launcher tube 12/54 inpairs (e.g. pellets 34 d and 34 f together, and then pellets 34 c and 34e).

FIG. 8D shows a two-part alternative structure for the inner sleeve 74that was disclosed above and is shown in FIG. 8A. Specifically, for thisembodiment, a distal inner sleeve 74′ and associated abutment 76′ areshown in axial alignment with the inner sleeve 74 and its abutment 76.For both embodiments, the object is to control compression of the spring32 (compare FIG. 8E with FIG. 8B).

Referring now to FIGS. 9A and 9B, yet another embodiment of a latchingmechanism for the launcher 10 of the present invention is shown. In thisembodiment, the launch tube 12/54 is formed with at least one lateralopening 86, and a clip 88 is mounted on a cylindrical shaped retainerplug 90. When the retainer plug 90 and its clip 88 are positioned in thelumen 28 of a launch tube 12/54, and the clip 88 is received in thelateral opening 86 of the launch tube 12 (see FIG. 9A), the clip 88 willhold the retainer plug 90 stationary in the launch tube 12/54.Specifically, this will be in response to forces imposed on the retainerplug 90 by a spring 32 (not shown in FIGS. 9A and 9B). Importantly, theclip 88 will not extend beyond the lateral opening 86. As with the otherlatching embodiments for the present invention, the retainer plug 90 isacceleration activated. Thus, in response to the acceleration force of alaunch, the retainer plug 90 moves in a proximal (rearward) direction.This then frees the clip 88 from the lateral opening 86 for subsequentfree travel of the retainer plug 90 through the launch tube 12/54 alongwith the propulsion of pellets 34 a (et. seq.) from the launch tube12/54.

In yet another configuration for components inside the launch tube12/54, a spring guide 92 is employed to control and restrict compressionof the spring 32. As shown in FIG. 10, the spring guide 92 includes abase 94 and an extension 96 which projects from the base 94. A throughhole 98 is formed in the spring guide 92, and this through hole 98extends through both the base 94 and the extension 96. Preferably, thespring guide 92 is made of a rigid, light-weight material such aspolycarbonate.

FIGS. 11A and 11B show how a spring guide 92 is employed by the presentinvention. First, in FIG. 11A, it will be seen that a pair of springguides 92 are used with the spring 32. Specifically, there is a distalspring guide 92 a and a proximal spring guide 92 b that are respectivelyengaged with opposite ends of the spring 32. As shown in FIG. 11A, bothof the spring guides 92 a and 92 b are positioned in the launch tube12/54 with their respective extensions 96 inserted into the center spaceof spring 32. Further, the base 94 of distal spring guide 92 a ispositioned against the pellet(s) 34, and the base 94 of proximal springguide 92 b is positioned against the abutment 76 at the proximal end 56of the launch tube 12/54. As shown in FIG. 11A, the configuration of thespring 32 with the spring guides 92 a and 92 b is prior to a launch.After launch, the spring 32 is compressed substantially as shown in FIG.11B by the acceleration force of the launch. Importantly, thiscompression of spring 32 is limited during an acceleration by thecontact that occurs between the extension 96 of spring guide 92 a andthe extension 96 of spring guide 92 b. A consequence of this is that thespring guides 92 a and 92 b help prevent a fouling of the spring 32during its operation.

Referring now to FIG. 12A, an alternate embodiment of a system forfiring the launcher 10 is shown, and is generally designated 100. Asshown, the system 100 includes a stabilizing section 102 and a payloadsection 104. In particular, the payload section 104 includes amulti-pellet launcher 10, as disclosed above, which has been modified toincorporate an insert extension 106. In all other important respects,the launcher 10 is substantially the same as disclosed earlier. Thestabilizing section 102, however, is unique unto itself.

Functionally, the stabilizing section 102 (see FIG. 12A) is effectivelythe same as an ordinary arrow that would be used with a conventional bow22. Also, the stabilizing section 102′ (see FIG. 12B) can be dimensionedas a bolt that would be used with a crossbow 20. Structurally, as shownfor the system 100 in FIG. 12A, the stabilizing section 102 for bothembodiments includes a shaft 108 that has an empennage 110. A fletching112 is provided as part of the empennage 110. At the forward end 114 ofthe shaft 108 is a connector 116 that is formed with an insertreceptacle 118. As intended for the present invention, for theembodiment as shown in FIG. 12A, an assembly of the system 100 merelyrequires a user to insert the insert extension 106 of the payloadsection 104 into the insert receptacle 118 of the payload section 104.Preferably, this insertion results in a “friction” or “interference” fitbetween the insert extension 106 of the payload section 104, and theinsert receptacle 118 of the stabilizing section 102. As intended forthe present invention, after a use of the system 100, and after pellets34 have been released from the launcher 10, the payload section 104 canbe removed from the stabilizing section 102. The stabilizing section 102can then be reused, and a different payload section 104 can then be usedwith this same stabilizing section 102.

For an alternate embodiment of the system 100 as shown in FIG. 12B, theinsert extension 106′ of the payload section 104 is shown to include apin 120. Further, the connector 116′ of the stabilizing section 102 isshown to include a slot 122 that is formed with a detent 124.Specifically, the slot 122 is axially aligned along the length of theshaft 108′ and is dimensioned to receive the pin 120. Thus, a so-called“bayonet” connection is established wherein the pin 120, after beinginserted into the slot 122 and advanced in a proximal direction towardthe empennage 110, can be rotated into the detent 124. Again, as withthe embodiment shown in FIG. 12A and disclosed above, after a use of thesystem 100, the payload section 104 can be removed from the stabilizingsection 102. Again, the stabilizing section 102 can be reused, and adifferent payload section 104 can then be used with the same stabilizingsection 102.

As envisioned for the system 100, the length “L” (see FIG. 12A) betweenthe empennage 110 and the connector 116 of the stabilizing section 102can be established depending on its intended use. For a conventional bow22, the length “L” will be equivalent to a typical arrow (e.g. FIG.12A), and will be somewhere around thirty two inches. On the other hand,the length “L” may be more equivalent to a bolt (e.g. see FIG. 12B) thatis to be shot from a crossbow 20. In this latter case the length “L”will be somewhere around four inches.

While the particular Arrow for Aerodynamically Stabilizing a Payload inFlight as herein shown and disclosed in detail is fully capable ofobtaining the objects and providing the advantages herein before stated,it is to be understood that it is merely illustrative of the presentlypreferred embodiments of the invention and that no limitations areintended to the details of construction or design herein shown otherthan as described in the appended claims.

What is claimed is:
 1. An arrow for aerodynamically stabilizing apayload during its flight along a flight path which comprises: a shaftdefining a longitudinal axis and having an aft-end and a fore-end; aplurality of fletches attached to the aft-end of the shaft to establishan empennage for stabilizing the shaft during flight; and a connectoraffixed to the fore-end of the shaft for selective engagement with apayload to hold the payload on the arrow during flight.
 2. An arrow asrecited in claim 1 wherein the payload is a multi-pellet launcher.
 3. Anarrow as recited in claim 1 wherein the payload is formed with an insertextension and the connector is formed as an insert receptacle forreceiving the insert extension therein to hold the payload on the arrow.4. An arrow as recited in claim 3 wherein the engagement of the payloadwith the arrow is a friction fit.
 5. An arrow as recited in claim 3wherein the engagement of the payload with the arrow is a bayonet fit.6. An arrow as recited in claim 1 wherein the empennage is athree-fletch assembly.
 7. An arrow as recited in claim 1 wherein theshaft is greater than four inches in length.
 8. An arrow as recited inclaim 1 wherein the shaft is less than thirty-two inches in length.
 9. Asystem for launching a pellet-cluster onto a flight path, using aman-powered weapon, the system comprising: a payload section to carrythe pellet-cluster for an in-flight release of the pellet-cluster fromthe payload section; and a stabilizer section, selectively engageablewith the payload section to aerodynamically stabilize the payloadsection on the flight path after launch from the man-powered weapon, andto maintain stabilization of the payload section until thepellet-cluster is separated in flight from the payload section.
 10. Asystem as recited in claim 9 wherein the payload section comprises: ahollow launch tube having a distal end and a proximal end with a lumenextending therebetween; a retainer plug positioned in the lumen of thelaunch tube; a plurality of pellets comprising the pellet-cluster, withthe pellet-cluster positioned in the lumen of the launch tube proximalto the retainer plug; a spring fixedly mounted in the lumen of thelaunch tube proximal the plurality of pellets; and anacceleration-activated latch having a first configuration wherein thelatch connects the retainer plug with the launch tube to hold theretainer plug stationary in the launch tube, and a second configurationwherein the latch releases the retainer plug from the launch tube forfree travel of the retainer plug through the lumen of the launch tube,and further wherein an acceleration force generated by a rapidacceleration of the launch tube in a distal direction transitions thelatch from its first configuration to its second configuration andcompresses the spring to propel the retainer plug and the pellet-clusterfrom the launch tube in the distal direction when the acceleration forcesubsides.
 11. A system as recited in claim 9 wherein the stabilizersection comprises: a shaft defining a longitudinal axis and having anaft-end and a fore-end; a plurality of fletches attached to the aft-endof the shaft to establish an empennage for stabilizing the shaft duringflight; and a connector affixed to the fore-end of the shaft forselective engagement with the payload section, to hold the payloadsection on the stabilizer section during flight.
 12. A system as recitedin claim 9 wherein the payload section is formed with an insertextension and the stabilizer section is formed as an insert receptaclefor receiving the insert extension therein to hold the payload sectionon the stabilizer section.
 13. A system as recited in claim 12 whereinthe engagement of the payload section with the stabilizer section is afriction fit.
 14. A system as recited in claim 11 wherein the empennageis a three-fletch assembly.
 15. A system as recited in claim 11 whereinthe shaft is greater than four inches in length.
 16. A system as recitedin claim 11 wherein the shaft is less than thirty-two inches in length.17. A method for assembling a system for launch from a man-poweredweapon, to aerodynamically stabilize a payload section of the systemduring flight on a flight path, the method comprising the steps of:providing an arrow having a shaft defining a longitudinal axis andhaving an aft-end and a fore-end, with a plurality of fletches attachedto the aft-end of the shaft to establish an empennage for stabilizingthe shaft during flight, and with a connector affixed to the fore-end ofthe shaft; and engaging a payload section with the connector of thearrow, wherein the payload section carries a pellet-cluster and isengaged with the arrow to aerodynamically stabilize the payload sectionon the flight path after launch from the man-powered weapon, and tomaintain stabilization of the payload section until the pellet-clusteris separated in flight from the payload section.
 18. A method as recitedin claim 17 further comprising the step of selecting a payload sectionhaving a desired number of pellets in the pellet-cluster.
 19. A methodas recited in claim 17 wherein the man-powered weapon is selected from agroup comprising a convention bow, a compound bow, a crossbow, and anair gun.
 20. A method as recited in claim 17 wherein the payload sectionis formed with an insert extension and the arrow is formed as an insertreceptacle for receiving the insert extension therein to hold thepayload section on the arrow and wherein the engagement of the payloadsection with the arrow is a friction fit.